摘要
利用系统动力学分析方法计算了导弹起落架所承受的载荷;运用多种单元形式建立了起落架复杂结构有限元分析模型,基于动力学计算所得载荷以及复杂约束条件,计算了导弹发射时起落架结构刚强度,检验了起落架结构安全性和设计合理性.计算结果表明起落架最大应力部位存在安全隐患,与试验情况吻合,该工作为导弹起落架设计与修改提供了理论依据.
The load on multi-missile load undercarriage was calculated using system dynamic simulation method. Finite element model of complex undercarriage structure in various unit was created. Load results from dynamic simulation and complex constrain were considered.The stiffness and intensity of missile undercarriage during launch were calculated based on the load and constrain obtained by dynamic calculation. The safety and design rationality of undercarriage structure were verified. Finite element results indicate that the position of maximum stress is not safe. It agrees with the practical situation. The study can provide design of missile undercarriage and modification with theoretical foundation.
出处
《弹道学报》
EI
CSCD
北大核心
2007年第1期75-77,共3页
Journal of Ballistics
关键词
导弹起落架
动力分析
有限元
结构安全性
missile undercarriage
dynamic analysis
finite element method
structural safety
